Rocket Propulsion System Oxygen-Hydrogen Mixing Ratio Control
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Solution Overview
Problem
Rocket propulsion systems using hydrogen as fuel face high combustion temperatures, leading to thermal loading issues, particularly in water electrolysis systems where hydrogen and oxygen are produced in a stoichiometric mixture ratio, limiting efficiency and power.
Innovation Solution
The method involves operating the rocket propulsion system in alternating modes with different oxygen-to-hydrogen mass mixing ratios, allowing for stoichiometric combustion while maintaining materials within permissible thermal limits, by adjusting hydrogen and oxygen flows and using a catalyst chamber for stable ignition and a cooling duct for temperature management.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Power
If hydrogen and oxygen are burned in stoichiometric mixture ratio to achieve high energy yield, then specific impulse and power are improved, but combustion temperature becomes excessively high causing thermal loading of materials
Solution Approach 1:
The patent applies periodic action by alternating between two operating modes: a first mode with lower oxygen-to-hydrogen mass mixing ratio (below stoichiometric) and a second mode with higher oxygen-to-hydrogen mass mixing ratio (at or above stoichiometric). This periodic switching allows the system to achieve average stoichiometric combustion for high power while limiting peak combustion temperatures to protect materials
Solution Approach 2:
The patent implements dynamics by making the oxygen-to-hydrogen mass mixing ratio variable rather than fixed. The control system dynamically adjusts the mixing ratio between the two operating modes based on operational requirements, enabling the system to optimize between power output and thermal protection in real-time
2Temperature
If sub-stoichiometric oxygen-hydrogen mixture is burned to limit combustion temperatures, then material thermal loading is reduced, but overall power and efficiency of the propulsion system decrease
Solution Approach 1:
The patent uses periodic action to switch between sub-stoichiometric operation (first mode with lower mixing ratio) that protects materials and stoichiometric operation (second mode with higher mixing ratio) that maximizes power. This allows the system to achieve high average power output while maintaining acceptable peak temperatures
Solution Approach 2:
The patent applies parameter changes by varying the oxygen-to-hydrogen mass mixing ratio between two distinct values. By changing this critical parameter dynamically, the system can shift between temperature-limited operation and power-optimized operation to achieve both goals
Applied Scientific Principles
This section explains which scientific principles are used to turn an abstract innovation direction into a practical engineering solution.
Function Achieved in This Case
This approach increases the overall mass flow and thrust of the rocket propulsion system, achieving higher combustion temperatures without exceeding material temperature limits, thereby enhancing power and reliability.
Implementation Method 1
using a catalyst chamber for stable ignition
Implementation Method 2
using a cooling duct for temperature management
Implementation Method 3
the oxygen-hydrogen mixture is burned in the combustion chamber
Data Source
AI summary
A method for operating a rocket propulsion system comprises the steps of supplying oxygen to a combustion chamber, supplying hydrogen to the combustion chamber and combusting the oxygen-hydrogen mixture in the combustion chamber. The rocket propulsion system is operated alternately in a first operating mode, in which oxygen and hydrogen are supplied to the combustion chamber in a first mass mixing ratio of oxygen to hydrogen, and in a second operating mode, in which oxygen and hydrogen are supplied to the combustion chamber in a second mass mixing ratio of oxygen to hydrogen that is greater than the first mass mixing ratio.